EP0110766B1 - Pale pour propulseur d'aéronef - Google Patents

Pale pour propulseur d'aéronef Download PDF

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Publication number
EP0110766B1
EP0110766B1 EP83402231A EP83402231A EP0110766B1 EP 0110766 B1 EP0110766 B1 EP 0110766B1 EP 83402231 A EP83402231 A EP 83402231A EP 83402231 A EP83402231 A EP 83402231A EP 0110766 B1 EP0110766 B1 EP 0110766B1
Authority
EP
European Patent Office
Prior art keywords
zone
profile
blade
thickness
leading edge
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired
Application number
EP83402231A
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German (de)
English (en)
French (fr)
Other versions
EP0110766A1 (fr
Inventor
Jean-Jacques Thibert
Jean-Marc Bousquet
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Office National dEtudes et de Recherches Aerospatiales ONERA
Original Assignee
Office National dEtudes et de Recherches Aerospatiales ONERA
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Publication date
Application filed by Office National dEtudes et de Recherches Aerospatiales ONERA filed Critical Office National dEtudes et de Recherches Aerospatiales ONERA
Publication of EP0110766A1 publication Critical patent/EP0110766A1/fr
Application granted granted Critical
Publication of EP0110766B1 publication Critical patent/EP0110766B1/fr
Expired legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/16—Blades
    • B64C11/18—Aerodynamic features
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/02—Formulas of curves

Definitions

  • the present invention relates to propellers for aircraft thrusters and, more particularly, the blades for such propellers.
  • the present invention aims to provide a propeller blade that better meets the requirements of practice than the blades known to high relative Mach numbers, especially between 0.8 and 0.9. It aims more particularly to delay the appearance of transonic phenomena, such as the formation of intense shock waves and the separation of the boundary layer, until higher relative Mach numbers.
  • a sail profile by a thickness variation law and a camber law along the chord c of the profile (line segment connecting the leading edge at the trailing edge).
  • the mean line of the profile, or "skeleton”, is the line such that each of its points is equidistant from the upper surface and the lower surface of the profile.
  • the thickness of the profile is, at each point of the mean line, the distance between the upper surface and the lower surface.
  • the law of thickness can be represented by a curve traced in a system of Cartesian coordinates where one carries on the abscissa the position of each point along the chord and, on the ordinate, the half-thickness at this point.
  • the curve thus obtained corresponds to half of a symmetrical profile in accordance with the law of thickness shown.
  • Other profiles of different relative thickness e max / c can be deduced therefrom by multiplication of the ordinates by a factor equal to the ratio of the maximum thicknesses e max (to the master couple) of the profile to be generated and of the basic profile.
  • the invention proposes, to solve the particular problem of a propeller, a blade according to claim 1.
  • the internal part may consist of a classic NACA profile and a progressive connection area.
  • the propeller blade profile is defined not only by the thickness variation law defined above, but also by the camber law of the mean line of the profile. This camber has a preponderant role on the lift of the blade. We will see later that with an appropriate camber one obtains an excellent value of the Mach number of drag divergence (Mach number from which the drag increases suddenly) for lift levels corresponding to the cruising speed of the equipped aircraft of the propeller, together with high maximum lift levels for lower Mach numbers, around 0.6 for example, which gives the propeller comprising blades according to the invention a level of efficiency also very high for takeoff and climb regimes.
  • Mach number of drag divergence Machine number from which the drag increases suddenly
  • this approximately linear decrease relates to the curvature of the law of variation of thickness, and not the curvature of the upper surface or the lower surface, which will depend in particular on the camber and the relative thickness. It is only in the case of a symmetrical profile and for a particular maximum relative thickness, that the curvature of the inside (and of the upper surface coincides with that of the law of profile thickness.
  • Each symmetrical profile can serve as a basis for generating a family of profiles by giving each member of the family the corresponding law of curvature.
  • the second zone advantageously extends between approximately 8% and 32% of the length of the cord and the curvature decreases in this second zone from a value of the order of 14 e max iC up to '' at a value substantially equal to 1.5e max / C, e max / C being the maximum relative thickness of the profile, to the master torque.
  • the external part at least of a propeller blade having a maximum relative thickness of between approximately 2 and 6%, has a profile whose law of variation of thickness along the cord has a first zone going from the leading edge to about 8% of the length of the cord, in which the curvature decreases rapidly from a maximum value equal to about 0.5 c / (e max ) 2 at the leading edge up to a value substantially equal to 14th max / C at the end of said first zone, followed by a second zone extending between approximately 8% of the rope and the master couple (advantageously approximately 32% of the cord) in which the curvature decreases linearly from a value substantially equal to 14th max / C to a value substantially equal to 1.5e max / C.
  • the second zone of the thickness law is extended to the trailing edge by a connection part.
  • This part may advantageously correspond to a third zone and a fourth zone where the laws of thickness are different.
  • the curvature is substantially constant, equal to around 1.5 e max iC in the case provided for in the previous paragraph.
  • This third zone further favors the control of the flow along the profile at high Mach numbers. This results in an increase in the extent of the supersonic zone with the Mach number, without increase in the intensity of the recompression shock wave terminating the supersonic zone and, downstream of the shock wave, small recompression gradients which avoid the separation of the boundary layer.
  • the fourth zone extending from the end of the third zone (typically 80% of the cord) to the trailing edge, has a reversal of curvature.
  • This particular evolution of the curvature, in this fourth zone, causes a re-acceleration of the flow in the final part (typically about the last ten percent) of the rope just before the trailing edge, thus helping to delay the appearance of detachments and to obtain low levels of drag.
  • the profile of a blade is defined not only by the thickness variation law which has just been considered, but also by its camber. Since the thickness variation law defined above makes it possible to obtain levels of lift coefficient higher than those of conventional profiles, it is possible to adopt a skeleton having a camber lower than that of a conventional profile, for a given maximum lift coefficient.
  • the maximum camber ap of the skeleton of a profile according to the invention can be chosen between 0.75 and 0.85a c (typically approximately 0.82a c ), a c representing the maximum camber of the skeleton of a classic profile, for example NACA series 16.
  • the point of maximum camber is advantageously located in a range extending over 10% of the chord around the master torque. It can be located approximately 35% of the chord from the leading edge, whereas one is generally led to place the maximum camber a c of the conventional profiles of the NACA 16 series at 50% of the chord; the corresponding maximum camber may be of the order of 0.0136 C. Due to the reduction in the maximum camber and its forward deflection, the profile according to the invention has, for a maximum lift coefficient at least equal to the maximum lift coefficients of conventional profiles, a lower moment coefficient c m , which reduces the torsional forces of the blade which are detrimental to its mechanical strength.
  • Fig. 1 which is a graphic representation of a thickness law according to the invention, can be viewed as showing a symmetrical profile having this thickness law: this profile has a leading edge 12 and a trailing edge 13 connected by a symmetrical upper surface 14 and a lower surface 15, convex for the most part but concave near the trailing edge 13.
  • the abscissa axis Ox is confused with the skeleton and the rope and the origin 0 is confused with the edge d attack 12.
  • the axis Ox is oriented positively from the leading edge 12 towards the trailing edge 13, the axis Oy being positively oriented from the lower surface 15 towards the upper surface 14.
  • the profile can be re kept as comprising four successive zones I, II, III and IV.
  • the first zone 1 begins at the leading edge 12, shown on a large scale in FIG. 2.
  • This first zone shows a rapid decrease in curvature.
  • the first zone will have a maximum curvature corresponding to the radius of the circle.
  • the curvature decreases linearly.
  • U 1 , Vietnamese, U 7 are constant coefficients, y and x being related to the length C of the chord.
  • the coefficients of formula (1) have approximately the values:
  • the second zone II which extends from point 16 to a point 17 where the thickness of the profile is maximum, advantageously located at an abscissa equal to approximately 32% of the chord, exhibits a substantially linear decrease in curvature from a value 14th max / C at point 16 to a value equal to 1.5e max / C at point 17, at the end of the second zone II, as shown in fig. 3.
  • Fig. shows that, compared to the law of thickness of a classic profile of the NACA 16 family, the law of thickness according to the invention makes it possible to obtain shock waves which are less intense and located more upstream, which delays the appearance of the separation of the boundary layer and ensures a low level of drag at high Mach numbers.
  • Zones III and IV can be represented by the formula (2) below between the master torque and the trailing edge:
  • camber can be represented, like the law of thickness, by a curve in a system of axes, the axis Ox of which coincides with the cord and the axis OA of ordinates is oriented from the lower surface towards the extrados.
  • This law of camber can be broken down into three zones represented by functions, for example polynomials.
  • the coefficients can have the following approximate values:
  • Fig. 6 shows the variation in the reduced camber a along the chord for a profile conforming to equations (3), (4) and (5) above, and for the values of the coefficients given by way of examples, it that is, the zones I a , II a and III a of the mean line are defined by the equations:
  • FIG. 7 shows an asymmetrical profile in accordance with the invention, that is to say associating a law of camber and a law of thickness of the kind given above.
  • fig. 8 shows the results of comparative wind tunnel tests carried out on a profile according to the invention, of the kind shown in FIG. 7, and on a conventional profile of reference NACA 16304 (of maximum relative thickness 4%).
  • the increase in drag as a function of the Mach number is much delayed on the profile according to the invention (curve U) compared to the NACA profile (curve V).
  • Fig. 9 shows that there is also a gain on the coefficient of moment C m .
  • the curves which give the variation of the moment coefficient C m as a function of the lift C z for Mach 0.85, show a reduction of the moment of about 70% (curve A) compared to the NACA profile (curve B).
  • fig. 10 which gives the lift values C z obtained for various incidences using the profile according to the invention (curve C) and for the reference profile (curve D) show that the lift levels are substantially the same, therefore that the gain on the other characteristics is not accompanied by any deterioration in the lift.
  • the invention therefore makes it possible to define the successive profiles of a high performance propeller blade applicable to any type of aircraft thruster.
  • the profiles according to the invention will generally be used only in the external part of the propeller blades, from the relative radius 0.6 and even often from the relative radius 0.7 only.
  • the internal part may for example have a NACA series 65 profile at the root and a connection area near the profiles according to the invention.
  • the relative thickness may also change from the root to the end of the blade.
  • the propeller blades will generally have a variable angle of arrow, increasing notably in the external part of the blade. It is thus possible to extend up to cruising Mach numbers of approximately 0.85 the field of use of the propellers.

Landscapes

  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
  • Tires In General (AREA)
  • General Details Of Gearings (AREA)
  • Retarders (AREA)
EP83402231A 1982-11-18 1983-11-18 Pale pour propulseur d'aéronef Expired EP0110766B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8219337A FR2536365A1 (fr) 1982-11-18 1982-11-18 Pale pour propulseur d'aeronef
FR8219337 1982-11-18

Publications (2)

Publication Number Publication Date
EP0110766A1 EP0110766A1 (fr) 1984-06-13
EP0110766B1 true EP0110766B1 (fr) 1987-06-24

Family

ID=9279296

Family Applications (1)

Application Number Title Priority Date Filing Date
EP83402231A Expired EP0110766B1 (fr) 1982-11-18 1983-11-18 Pale pour propulseur d'aéronef

Country Status (6)

Country Link
US (1) US4652213A (enExample)
EP (1) EP0110766B1 (enExample)
JP (1) JPS59118597A (enExample)
DE (1) DE3372195D1 (enExample)
FR (1) FR2536365A1 (enExample)
SU (1) SU1540653A3 (enExample)

Families Citing this family (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
USRE33589E (en) * 1986-09-03 1991-05-14 United Technologies Corporation Helicopter blade airfoil
US4744728A (en) * 1986-09-03 1988-05-17 United Technologies Corporation Helicopter blade airfoil
US4834617A (en) * 1987-09-03 1989-05-30 United Technologies Corporation Airfoiled blade
FR2628062B1 (fr) * 1988-03-07 1990-08-10 Aerospatiale Pale pour helice carenee a hautes performances, helice carenee multipale pourvue de telles pales et agencement de rotor de queue a helice carenee pour aeronef a voilure tournante
GB2220712B (en) * 1988-07-13 1992-12-09 Rolls Royce Plc Open rotor blading
US5024396A (en) * 1988-07-19 1991-06-18 Principia Recherche Developpement Sa Air or submarine engine with improved contour
US4941803A (en) * 1989-02-01 1990-07-17 United Technologies Corporation Airfoiled blade
JP2633413B2 (ja) * 1991-06-03 1997-07-23 富士重工業株式会社 回転翼航空機の回転翼羽根
FR2689852B1 (fr) * 1992-04-09 1994-06-17 Eurocopter France Pale pour voilure tournante d'aeronef, a extremite en fleche.
WO1994008846A1 (fr) * 1992-10-16 1994-04-28 Aktsionernoe Obschestvo 'aviatika' Helice
US5417548A (en) * 1994-01-14 1995-05-23 Midwest Research Institute Root region airfoil for wind turbine
RU2123453C1 (ru) * 1996-12-15 1998-12-20 Центральный аэрогидродинамический институт им.проф.Н.Е.Жуковского Лопасть винта
US5911559A (en) * 1997-09-16 1999-06-15 United Technologies Corporation Airfoiled blade for a propeller
US6378802B1 (en) * 1998-05-04 2002-04-30 Manuel Munoz Saiz Enhance aerodynamic profile
US6607164B2 (en) 2001-10-22 2003-08-19 Toyota Motor Sales, U.S.A., Inc. Wing airfoil
ES2268912B1 (es) * 2003-03-13 2008-02-16 Indar Maquinas Hidraulicas, S.L Grupo electrobomba multietapa.
US20040206852A1 (en) * 2003-04-16 2004-10-21 Saiz Manuel Munoz Aerodynamic profile
IT1401661B1 (it) * 2010-08-25 2013-08-02 Nuova Pignone S R L Forma di profilo areodinamico per compressore.
US9340277B2 (en) * 2012-02-29 2016-05-17 General Electric Company Airfoils for use in rotary machines
DE102013008145A1 (de) * 2013-05-14 2014-11-20 Man Diesel & Turbo Se Laufschaufel für einen Verdichter und Verdichter mit einer solchen Laufschaufel
US9278744B1 (en) 2015-03-26 2016-03-08 Frank Chester ChetProp air or water propeller and spinner with front and back leg assemblies attached to spinner
CN105129071B (zh) * 2015-06-26 2017-03-08 北京昶远科技有限公司 太阳能飞机翼型设计方法及太阳能飞机翼型
US10710705B2 (en) * 2017-06-28 2020-07-14 General Electric Company Open rotor and airfoil therefor
US10358926B2 (en) * 2017-08-11 2019-07-23 General Electric Company Low-noise airfoil for an open rotor
FR3077803B1 (fr) * 2018-02-15 2020-07-31 Airbus Helicopters Methode d'amelioration d'une pale afin d'augmenter son incidence negative de decrochage
EP3891066A4 (en) * 2018-12-07 2022-08-10 Joby Aero, Inc. ROTATING AIRFORCE AND DESIGN METHOD THEREFORE
WO2021092677A1 (en) * 2019-11-14 2021-05-20 Delson Aeronautics Ltd. Ultra-wide-chord propeller
RU2769545C1 (ru) * 2021-05-14 2022-04-04 Акционерное общество "Национальный центр вертолетостроения им. М.Л. Миля и Н.И. Камова" (АО "НЦВ Миль и Камов") Аэродинамический профиль несущего элемента летательного аппарата

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3343512A (en) * 1966-05-20 1967-09-26 Francis R Rasmussen Hydrofoil with unsymmetrical nose profile
GB1383070A (en) * 1971-12-13 1975-02-05 Boeing Co Hydrodynamic sections
US4142837A (en) * 1977-11-11 1979-03-06 United Technologies Corporation Helicopter blade
GB2016397B (en) * 1978-02-02 1982-03-24 Aerospatiale Aerofoil
US4459083A (en) * 1979-03-06 1984-07-10 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Shapes for rotating airfoils
FR2463054A1 (fr) * 1979-08-10 1981-02-20 Aerospatiale Profil de pale pour voilure tournante d'aeronef
FR2490586A1 (fr) * 1980-09-24 1982-03-26 Aerospatiale Profil de pale pour voilure tournante d'aeronef
US4412664A (en) * 1982-06-25 1983-11-01 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Family of airfoil shapes for rotating blades

Also Published As

Publication number Publication date
US4652213A (en) 1987-03-24
JPS59118597A (ja) 1984-07-09
EP0110766A1 (fr) 1984-06-13
FR2536365B1 (enExample) 1985-04-26
DE3372195D1 (en) 1987-07-30
FR2536365A1 (fr) 1984-05-25
SU1540653A3 (ru) 1990-01-30

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